Abstract
Based on studies about various concepts to control the shock boundary layer interference the adaptive SC bump seems to be the most efficient shock control device to reduce drag in the off-design condition. The influence of the bump geometry on the drag behaviour is numerically investigated using a DA laminar airfoil and verified by airfoil experiments in the ONERA wind tunnel T2. In spite of encouraging experimental results in drag reduction with a wing-body configuration equipped with a fixed bump in 3D flow condition, the practical application on wings is not solved due to design and integration problems.
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© 1999 Springer Science+Business Media Dordrecht
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Dargel, G., Rodde, A.M., Archambaud, J.R. (1999). Assessment of the Capability of Drag Reduction of the Shock Control Device ‘SC Bump’ on Airfoil Flows and Application Aspects on Wings. In: Meier, G.E.A., Viswanath, P.R. (eds) IUTAM Symposium on Mechanics of Passive and Active Flow Control. Fluid Mechanics and its Applications, vol 53. Springer, Dordrecht. https://doi.org/10.1007/978-94-011-4199-4_8
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DOI: https://doi.org/10.1007/978-94-011-4199-4_8
Publisher Name: Springer, Dordrecht
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